Integrated Propulsion System Modeling for Advanced Aircraft Using Multidisciplinary Design Optimization
Gas turbines will remain central to powering future transport aircraft, but their role within the propulsion system is expected to evolve. This talk presents an optimization-oriented propulsion modeling framework for integrated aircraft conceptual design. Parametric turbofan, turboshaft, and fan models are implemented in NASA's OpenMDAO environment using pyCycle and organized within a unified propulsion-system formulation.